WO2011067146A1 - Procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial et dispositif de déformation - Google Patents

Procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial et dispositif de déformation Download PDF

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Publication number
WO2011067146A1
WO2011067146A1 PCT/EP2010/068138 EP2010068138W WO2011067146A1 WO 2011067146 A1 WO2011067146 A1 WO 2011067146A1 EP 2010068138 W EP2010068138 W EP 2010068138W WO 2011067146 A1 WO2011067146 A1 WO 2011067146A1
Authority
WO
WIPO (PCT)
Prior art keywords
forming
belt
preform
sections
tool
Prior art date
Application number
PCT/EP2010/068138
Other languages
German (de)
English (en)
Inventor
Marek Beresinski
Original Assignee
Airbus Operations Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations Gmbh filed Critical Airbus Operations Gmbh
Priority to EP10781516.9A priority Critical patent/EP2507038B1/fr
Priority to CN201080054462.1A priority patent/CN102666076B/zh
Publication of WO2011067146A1 publication Critical patent/WO2011067146A1/fr
Priority to US13/483,561 priority patent/US9375882B2/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0003—Producing profiled members, e.g. beams
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C2793/00—Shaping techniques involving a cutting or machining operation
    • B29C2793/0081—Shaping techniques involving a cutting or machining operation before shaping
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49616—Structural member making
    • Y10T29/49622—Vehicular structural member making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/51—Plural diverse manufacturing apparatus including means for metal shaping or assembling

Definitions

  • the present invention relates to a method for forming a structural component of an air or space ⁇ vehicle and to a forming device.
  • CFRP carbon fiber plastic
  • braided profiles are to be treated.
  • Today's braiding technology allows the production of braids, which are characterized by closed cross-sections.
  • a core for example, with a rectangular profile
  • braided with fibers with braided layers arise.
  • belt layers eg unidirectional fiber layers
  • a braided hollow profile for example a rectangular tube with a closed cross-section
  • this rectangular profile is then divided in a plane in its longitudinal axis so that two C-profiles are formed.
  • preform is molded to understand a so-called preform or textile fiber intermediates, which subsequently impregnated with a matrix and then, for example be in an autoclave ⁇ cured.
  • the present invention has for its object to provide an improved method for the Bil a structural component of an aircraft or Spacecraft ⁇ sat. Another object is to provide a corresponding forming device.
  • this object is achieved by a method having the features of patent claim 1 or by a forming device having the features of the patent claim.
  • a preform comprising at least one belt is formed by braiding a core.
  • the preform is a separating section at least section-wise of the Minim from ⁇ ⁇ least introduced a belt for forming two belt portions.
  • a forming device serves to carry out the method.
  • a structural component is produced by the method and / or by means of the shaping device.
  • a forming device for forming a structural component of an aircraft or spacecraft is provided ⁇ . It has the following
  • a tool body having a receptacle for receiving a braided preform having at least one belt
  • At least one cutting means for introducing a separating cut at least in sections in the Minim ⁇ least one strap of the preform to form two belt portions of the at least one belt;
  • At least one deformable along the separating cut forming tool for forming the two formed belt portions of the at least one belt (3, 4) in a pre ⁇ certain form.
  • the present invention over the approaches mentioned above has the advantage that the auto ⁇ mated braiding technique is also suitable for the production of braiding by hitherto not producible profiles with all its advantages.
  • a basic idea of the invention is, by simp ⁇ ches editing, for example, introducing a separation Cutting in a preform, as a preparation to transform this so that a new profile from the Kirpro ⁇ fil arises.
  • a transformation or transformation of a braided preform for example from a pre ⁇ molding for a C-profile in a Z-profile
  • the Beibe ⁇ hold the fiber orientation in the affected reshaped layers is of great importance.
  • the belt with the smaller diameter and below the outer belt should be understood to mean the belt with the larger diameter.
  • the outer girth the
  • Fibers during forming forced to adapt to the large radius, ie they are pulled. With multiple layers and a fiber orientation of ⁇ 45 ° or 90 °, this can lead to local fiber gaps. Once the fibers are in 0 ° between the diagonals, they are trying to during forming inwardly to various ⁇ ben because the length of the fiber remains the same. But if the inner belt is formed, then the fibers are ge ⁇ upsized, which can lead to local folds during the forming process. The change in the transition radius at the individual layers can also lead to shifts between the layers, ie it must be possible to shift the layers between each other without undulating the fiber.
  • the invention provides that the core is braided with at least two braid layers, wherein the at least one belt is provided with separating layers between each two braid layers. It is advantageous if these separating layers are formed, for example, of release film.
  • preforms with more than one belt for example with an outer and an inner belt, not only the outer belt, but also the inner belt can be transformed.
  • the braids formed on the basis of individual preforms can also provide a number of components differing slightly from one another, since the final geometry is determined only during the forming process.
  • the forming takes place in layers by folding over the formed belt sections. This significantly reduces the risk of fiber gaps and imperfections. It is important that the fibers of the overall braided layers retain their fiber orientation during forming and not be damaged by the forming tool ⁇ the.
  • the separating layers continue to provide the advantage that they protect the fibers to be reshaped from damage, for example by a forming tool during forming. They also allow for layerwise folding a slight separation of the individual layers from each other.
  • the respective separating layers are removed after each layer-wise folding of belt sections and replaced by previously prepared belt layers, eg unidirectional (UD) fiber fabrics, which are then fixed. This can be done for example by a removal device which cooperates with a laying device or is arranged together.
  • UD unidirectional
  • a tool body of the forming device can have corresponding concave and / or convex sections in the region of the layer sections to be formed, wherein the shaping tool can be equipped for this purpose with corresponding pressing devices, eg pressure rollers.
  • a shaped preform is thus formed.
  • another belt or another, predetermined portion in the longitudinal direction of the formed preform can be separated to obtain two separate, formed preforms.
  • a ⁇ profile can be produced from a braided rectangular profile by first separating the inner belt and reshaping the associated belt sections. By second separation of the ande ⁇ ren belt one then obtains two Z-profiles. The entire process can proceed almost completely advantageously au ⁇ automatically, whereby the conditions for industrial implementation are met.
  • This forming technology opens up completely new applications of straw ⁇ procedure with its own advantages, since in the
  • the forming device has at least one removal device for removing the separating layers and a laying device for laying belt layer sections on the formed preform.
  • the laying device can be combined with a removal device for the separating layers at the same time, an automated process being advantageously accelerated.
  • the forming tool has a shape of a plow or a snow with mallli ⁇ chen forming surfaces that on ⁇ run in the longitudinal direction of the forming tool at a predetermined angle to each other, wherein they at a front side of the forming tool in a cutting are connected.
  • the forming surface of the forming tool having a web with at least one throat, wherein the Keh ⁇ le merges at its upper end in a guide surface.
  • a radius of the throat has a relatively small value.
  • the forming surfaces of the forming tool are configured to form a predetermined deformation of the portions of the preform to be formed accordingly.
  • the forming surface of the forming tool is so formed that a distance of fibers of the reshaped portions of the preform to a central axis of the preform during the molding operation is order ⁇ minimal.
  • the forming tool may comprise the cutting device.
  • this cutting device can be mounted in the web on the front side of the forming tool by forming this edge as a cutting edge.
  • the cutter In forward ⁇ of the forming tool move the cutter is first cut through the braid layer of the belt and then umklap ⁇ pen.
  • the belt to be separated or its mesh layer can also be incised by a pre-cutter to facilitate the cutting process.
  • a structural component for aerospace is manufactured according to the method described above and / or by means of the above-described forming device.
  • Fig. 1 is a schematic, perspective cross-sectional viewing of a preform according to an off ⁇ execution example for explaining a ⁇ he inventive method
  • FIG. 2 shows the preform according to FIG. 1 after a further step of the method according to the invention
  • FIG. 3 shows the preform of Figure 2 after a further step of the inventive method with an exemplary embodiment of an inventive forming device he ⁇ ..;
  • FIG. 4a schematic, perspective views ei ⁇ nes embodiment of a Umformwerk- stuff with partial cuts;
  • Fig. 4d is a schematic perspective view of the forming tool according to Vorderan ⁇
  • Fig 4a-c is a schematic side view according to An ⁇ view A of the forming tool according to Fig. 4d.
  • FIG. 5 shows the preform according to FIG. 3 after a further step of the method according to the invention in the forming device according to the invention
  • FIG. 6 shows the deformed preform according to FIG. 5 after a further step of the method according to the invention in the forming device according to the invention.
  • Fig. 7 is a schematic sectional view of a ge ⁇ separated, reshaped preform.
  • Fig. 1 shows a schematic perspective sectional view ⁇ a preform 1 according of an exemplary embodiment for explaining a method according to the invention.
  • the preform ⁇ ling 1 is produced in a braiding process.
  • a core 2 here with a rectangular cross-section, is braided with fibers, in this example a three-layered material.
  • ger preform 1 is formed.
  • diagonal layers are produced, for example, as a biaxial or UD braid (UD means unidirectional), with a first inner braiding layer 7 lying directly on the core 2.
  • a center braid layer 8 is wound, which is braided by an outer braid layer 9.
  • the preform 1 has a curved structure, as shown in FIG. 1 can be seen. It has straps 3 and 4, WO 4 in the belt as internal belt and the belt 3 is called Au ⁇ infogurt. These straps are connected via Profilste ⁇ ge 5, 6.
  • the inner belt 4 is provided for forming, which is prepared by a separating cut 17 (see FIG. 2). Therefore, a release liner 12 is placed on the inner belt 4 instead of a belt layer.
  • the separating layer can be a separating film, for example.
  • the preform 1 is now made as a braided component with a closed cross section of the mesh layers 7 to 9.
  • the braiding takes place in a corresponding braiding device with individual fibers, a plurality of fibers and / or fiber bundles or the like.
  • the thus prepared preform 1 is then in a second process step, Fig. 2 illustrates, with a Cutting means forming part of a forming device 30 (see Fig. 3) may be processed such that the internal belt 4 is provided in the longitudinal direction ⁇ x of the preform 1 with a cut 17th
  • the separating cut 17 can take place simultaneously through all mesh layers 7 to 9. But it is also possible that the
  • Separation section 17 is performed in layers.
  • the disconnector according to section 17 can also be performed at any location with a suitable cutter.
  • the belt 4 in this case the inner belt 4 per woven layer, is divided into two belt sections, namely: two inner layer belt sections 14-1 and 14-2, two middle layer belt sections 15-1 and 15-2, and two Outer layer belt sections 16-1 and 16-2.
  • the separating layers 12 and 13 are also divided into separating layer sections 12-1 and 12-2 as well as 13-1 and 13-2.
  • the forming device 30 here has a tool body 31 with a receptacle 32, which on both sides in
  • Longitudinal x each have a tool top 33-1 and 33-2.
  • the preform 1 is inserted with its core 2 in the receptacle 32.
  • the prepared for transformation by the separation section 17 with its inner belt 4 ge ⁇ divided strap sections 14-1, 14-2, 15-1, 15-2, 16-1 and 16-2 protruding from the seat 32 upward.
  • the forming cross-section 21 is shown here only by way of example at a specific x-position of the longitudinal direction of the forming tool 20.
  • the outer-layer belt sections 16-1 and 16-2 are formed together with the second separating layer 13-1 and 13-2 by forming surfaces 26-. 1 and 26-2 (see Fig. 4a-d) guided and transformed so that they are first bent or folded in a small radius.
  • the outer-layer belt portions 16-1 and 16-2 finally complete (here folded by approximately 180 ° from its position herein are subject ⁇ ring) together with the second release liner 13-1 and 13-2 which is shown in Figs. 6 and 7 and described in more detail below.
  • the separating layers 12, 13 thereby protect the individual belt sections 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14-2 against damage by the forming tool 20. At the same time, they allow an easy separation of the braid ⁇ were during forming.
  • the forming tool 20 is out ⁇ forms that during forming the spacing of the fibers of the JE rion layer on tape segment 16-1 and 16-2, 15-1 and 15- 2, 14-1 and 14-2 to the central axis of the preform 1, which runs here in the longitudinal direction, ie in the x direction, are kept at a minimum distance.
  • the forming tool 20 is shown in Fig. 4a to 4c in schemati ⁇ rule, perspective views of an exemplary embodiment with partial sections. A front view il ⁇ lustriert Fig. 4d.
  • the forming tool 20 has an underside 28, which is correspondingly smooth and / or correspondingly is layered to ensure the lowest possible coefficient of friction between the bottom 28 and the layer belt sections 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14-2 and the separating layers 12, 13.
  • the forming tool 20 is in the form of a plow (here with two coulters) or a snow remover and formed in the top view ⁇ triangular. Its front face is illustrated in Fig.
  • FIGS. 4 a to 4 c illustrate the forming cross section 21 at different x positions of the longitudinal direction of the forming tool 20.
  • a respective throat 23-1, 23-2 is arranged, wherein the throat 23-1, 23-2 at its upper end via a Kehlenauslauf 25-1, 25-2 in a Füh ⁇ tion surface 24-1, 24-2 passes.
  • the throat 23-1, 23-2 is formed with a throat inlet 27-1, 27-2 and a bottom edge 29-1, 29-2, which has a special ⁇ DERS small radius, with which between the ply Belt portions 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14-2 is intervened to separate them from each other.
  • the throat 23-1, 23-2 extends at a Popemm th radius from the front of the forming tool 20 (see Fig. 4d) to its back (see Fig.
  • the throat outlet 25-1, 25-2 and the throat inlet 27-1, 27-2 on each longitudinal side of the forming tool 20 each have a forming surface 26-1, 26-2 for forming the respective layer belt portion 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14-2 when folding over the same.
  • the forming surfaces 26 - 1, 26 - 2 are arranged at an angle symmetrically to the center line of the forming tool 20, the center line extending in the x direction, ie the direction of movement of the forming tool 20.
  • the forming surfaces 26-1, 26-2 are corresponding to the material of the mesh layers 7, 8, 9 of a material which results in a friction pairing with an extremely low friction value.
  • the respective forming surface 26-1, 26-2 may also be coated, for example with Teflon®, as well as the underside 28 of the forming tool 20th
  • the forming surfaces 26-1 and 26-2 are connected to a front side of the forming die 20 in the cutting edge 22a.
  • Fig. 4d shows in a front view of the forming tool 20 whose plow-like shape. Of course, other shapes are possible.
  • the cutting edge 22a may also be formed as a sharp edge, to the separation section 17 or ⁇ a slicing a voreinge4.000e- NEN separation section 17 may separate.
  • FIG. 4e shows a side view A of the forming tool 20 according to FIG. 4d.
  • the guide surface 24-1 (24-2 also on the other side) with its outer edge of the cutting edge 22a, ie from the front of the forming tool 20 downwards at an angle inclined ei ⁇ angle to the rear runs.
  • this outer edge of the guide surface 24-1 passes over into the cutting edge 22a downwards.
  • the forming tool 20 abuts the forming device 30 a longitudinal guide (not shown), which follows the course of the preform 1, ie the tool body 31. It can be driven automatically, wherein a delivery in the z-direction is possible to make a layer-wise deformation of the layer belt sections 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14-2 ,
  • FIG. 5 shows the preform 1 according to FIG. 3 after a further step of the method according to the invention in the forming device 30 according to the invention.
  • the layer belt sections 16 - 1 and 16 - 2 have been folded over by the forming tool 20. In this example, they are be applied to the tool ⁇ tops 33-1 and 33-2 by about 180 °. Of course, other angles than 180 °, larger or smaller can be reshaped.
  • the separating layer sections 13-1 and 13-2 are removed (here already made in FIG. 5) and replaced by first belt layer sections 18-1, 18-2, which by a laying ⁇ device (not shown) on the folded layer belt sections 16-1 and 16-2 instead of the Trennlagenab ⁇ sections 13-1 and 13-2 are placed and fixed.
  • the belt layer sections 18-1, 18-2 are, for example, UD scrims prepared at another location.
  • the formed preform 1 thus obtained has a type of U-profile or else ⁇ -profile.
  • the tool body 31 can be part of a molding tool that can be closed for impregnating and curing the deformed preform 1.
  • Impregnated matrix material for example, and cured in an autoclave ⁇ , after which the core 2 is removed.
  • a further step may consist in (also before impregnation and curing possible) that now the outer belt 4 is separated by a second separating cut 34, resulting in two formed preforms 1-1 and 1-2 with Z-profile.
  • the separating cut 17 can be only a kind of scribing or incision of the respective braid layer 7 to 9 of the inner belt 4 in layers, the forming tool 20 with the advancing cutting edge 22a (FIG. 4d) completely separating the cut or pre-scored severing cut 17 in layers.
  • the second separating cut 34 can also take place at different points, so that, for example, the resulting Z-profiles are different and, in the extreme case, an L-profile and a Z-profile are obtained.
  • components with concave (and / or convex) surfaces can also be produced.
  • the tool top side 33-1, 33-2 can have concave indentations or convex protuberances at predetermined positions, against which the folded-over layer belt sections 16-1 and 16-2, 15-1 and 15-2, 14-1 and 14- 2 can be adjusted by the forming tool 20 with a corresponding extension, eg pressure rollers. Including forms can be generated ER- that would so not recoverable ⁇ bar by braiding.
  • the preform 1 can have only two mesh layers or even more.
  • the tool body 31 is such that it can be used simultaneously for forming the preform 1 as well as for impregnating and curing the deformed preform.
  • a preform 1 with a triangular cross-section is also conceivable, for example, one side forms a belt to be separated and serve the other two sides as webs.
  • Direction preform 1 is formed by braiding around a core. 2
  • a separation cut 17 at least from ⁇ cut to form two belt sections 14-1, 14-2; 15-1, 15-2; 16-1, 16-2 of the at least one belt 4 a ⁇ brought.
  • a forming tool 20 which can be guided along the separating cut 17, the two formed belt sections 14-1, 14-2 are then deformed. 15-1, 15-2; 16-1, 16-2 of the at least one belt 4 in one predetermined shape.
  • a forming device 30 serves to carry out the method.
  • a structural component is produced by the method and / or by means of the shaping device.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Braiding, Manufacturing Of Bobbin-Net Or Lace, And Manufacturing Of Nets By Knotting (AREA)

Abstract

Dans le cas d'un procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial, on forme une ébauche (1) présentant au moins une membrure (4) au moyen de tressage d'un noyau (2). Dans la au moins une membrure (4) de l'ébauche (1), on introduit une jointure (17) au moins par endroits pour former deux parties de membrure (14-1, 14-2 ; 15-1, 15-2 ; 16-1, 16-2) de la au moins une membrure (4). Au moyen d'un outil de déformation (20) pouvant être guidé le long de la jointure (17), on procède ensuite à une déformation des deux parties de membrure formées (14-1, 14-2 ; 15-1, 15-2 ; 16-1, 16-2) de la au moins une membrure (4) dans une forme prédéfinie. Un dispositif de déformation (30) sert à mettre en œuvre le procédé. Un composant de structure est fabriqué au moyen du procédé et/ou du dispositif de déformation.
PCT/EP2010/068138 2009-12-01 2010-11-24 Procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial et dispositif de déformation WO2011067146A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10781516.9A EP2507038B1 (fr) 2009-12-01 2010-11-24 Procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial, dispositif de déformation et composant de structure ainsi obtenu
CN201080054462.1A CN102666076B (zh) 2009-12-01 2010-11-24 形成飞行器或航天器结构部件的方法及其设备
US13/483,561 US9375882B2 (en) 2009-12-01 2012-05-30 Method for forming a structural component of an aircraft or spacecraft, and forming device

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US26547809P 2009-12-01 2009-12-01
DE102009047340A DE102009047340B4 (de) 2009-12-01 2009-12-01 Verfahren zum Bilden eines Strukturbauteils eines Luft- oder Raumfahrzeuges und Umformvorrichtung
DE102009047340.8 2009-12-01
US61/265,478 2009-12-01

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/483,561 Continuation US9375882B2 (en) 2009-12-01 2012-05-30 Method for forming a structural component of an aircraft or spacecraft, and forming device

Publications (1)

Publication Number Publication Date
WO2011067146A1 true WO2011067146A1 (fr) 2011-06-09

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PCT/EP2010/068138 WO2011067146A1 (fr) 2009-12-01 2010-11-24 Procédé pour former un composant de structure d'un aéronef ou d'un véhicule spatial et dispositif de déformation

Country Status (5)

Country Link
US (1) US9375882B2 (fr)
EP (1) EP2507038B1 (fr)
CN (1) CN102666076B (fr)
DE (1) DE102009047340B4 (fr)
WO (1) WO2011067146A1 (fr)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
WO2013152961A1 (fr) * 2012-04-12 2013-10-17 Airbus Operations Gmbh Procédé et dispositif permettant de produire une préforme textile

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DE102012004942B4 (de) * 2012-03-12 2014-02-20 Munich Composites Gmbh Verfahren zum Herstellen eines Vorformlings und eines daraus hergestellten Faserverbundfertigbauteils
US8758879B2 (en) * 2012-06-24 2014-06-24 The Boeing Company Composite hat stiffener, composite hat-stiffened pressure webs, and methods of making the same
DE102013220337A1 (de) * 2013-10-09 2015-04-09 Bayerische Motoren Werke Aktiengesellschaft Verfahren zum Herstellen eines verstärkten Faserverbundbauteils
DE102014000302B4 (de) * 2014-01-10 2015-10-08 Bayerische Motoren Werke Aktiengesellschaft Flechtlitze als Flachgeflecht
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US9375882B2 (en) 2016-06-28
US20120292448A1 (en) 2012-11-22
EP2507038B1 (fr) 2014-02-12
DE102009047340A1 (de) 2011-06-09
CN102666076A (zh) 2012-09-12
CN102666076B (zh) 2015-03-11
EP2507038A1 (fr) 2012-10-10
DE102009047340B4 (de) 2011-07-14

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